Aircraft turbine engine comprising an electric motor comprising a device for correcting a precession movement and associated method

An aircraft turbine engine comprising at least one propulsion shaft and an electric motor, a rotor of which is rigidly connected to the propulsion shaft, the electric motor comprising:

• a stator comprising at least three power channels, the rotor being configured to interact magnetically with the power channels,
• the electric motor being configured to operate in a generator mode in order to collect mechanical power from the rotor to generate electrical power and also to operate in a motor mode in order to consume the electrical power to generate mechanical power and drive the rotor,
• a control device configured to determine a control parameter for each of the power channels as a function of a control command, each of the control parameters defining currents circulating in the power channel, each of the power channels generating a magnetic force on the rotor which is a function of the control parameter, an assembly of the magnetic forces applied by the power channels on the rotor defining an overall magnetic force, and
• a correction device configured to correct a precession movement of the rotor relative to the stator, the correction device being configured for:
• determining a precession level of the rotor relative to the stator,
• determining the control command for the control device from a setpoint command and from the precession level, the control command being configured to generate an overall magnetic force opposing the precession movement of the rotor so as to damp the rotor.